By Zhuo Kang, Lishan Kang, Xiufen Zou, Minzhong Liu, Changhe Li, Ming Yang, Yan Li (auth.), Lishan Kang, Yong Liu, Sanyou Zeng (eds.)
This booklet constitutes the refereed complaints of the second one foreign Symposium on Intelligence Computation and functions, ISICA 2007, held in Wuhan, China, in September 2007. The seventy one revised complete papers have been conscientiously reviewed and chosen from approximately one thousand submissions. the subjects contain evolutionary computation, evolutionary studying, neural networks, swarms, development attractiveness, info mining and others.
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Extra resources for Advances in Computation and Intelligence: Second International Symposium, ISICA 2007 Wuhan, China, September 21-23, 2007 Proceedings
The next set of 4 variables are coded as real-valued variables and represent transfer times between departure planet to first swing-by planet, first to second swing-by planet, second to third swing-by planet and third swing-by to arrival planet. Here again, depending on the number of swing-by planets (S) dictated by the first two-bit substring, we consider only the first (S + 1) transfer times. A typical NSGA-II solution may look like the following: 10 000 100 101 16/6/2005 124 205 580 425 The solution signifies that there are two swing-by planets and they are the first planet (Mercury) and fifth planet (Jupiter) between departure and arrival planets (need not be represented in NSGA-II, as they are fixed for all feasible solutions).
The software displays a number of trade-off optimized solutions and allows user to investigate the trajectory through a graphical user interface. L. Kang, Y. Liu, and S. ): ISICA 2007, LNCS 4683, pp. 26–35, 2007. c Springer-Verlag Berlin Heidelberg 2007 Interplanetary Trajectory Optimization with Swing-Bys 27 2 Previous Studies on Interplanetary Trajectory Optimization The celestial mechanics of the ’swing-by’ is known to astronomers for at least 150 years. A lot of research work have been done in the area of Interplanetary Trajectory Optimization (IPTO), for both direct transfer and with swing-by of other planets.
2. Trade-off solutions for the Earth-Mars- Fig. 3. 45695e+06 Table 3. 4566e+06 NUMERIT SC GOSpel Min. Vel. Min. Time Dep. date 01/10/14 12/05/13 12/06/13 03/20/14 Arr. 132 50 Vel. 45655e+06 Fig. 4. Trade-off solutions for the Earth-Mars direct mission using GOSpel solution is better than the Numerit solution. Next, we apply GOSpel with a population size of 100 and run till 300 generations. The two extreme solutions are shown in table. It is interesting to note that the minimum launch velocity solution obtained by GOSpel is almost similar to that obtained by SC.
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